以某型高压九级轴流压气机为研究对象，通过NUMECA软件进行模拟计算，研究了前过渡段、过渡段支板和出口过渡段的气体流动损失对压气机性能的影响，并采用DFFD参数化方法和多岛遗传算法对过渡段部分进行了结构改型与气动优化设计。结果表明：相比不带过渡段的压气机模型，原型过渡段使等熵效率降低1.57%，经过对过渡段型线改进以及对过渡段支板的优化设计，优化后过渡段使等熵效率仅降低0.63%；优化后的过渡段部分气流阻塞减少、损失减小，使得高压压气机整体效率较优化前提高0.94%；经流场损失分析发现，支板段和出口扩压延长段是造成堵塞和效率降低的主要原因。

Taking a 9stage axial flow compressor of a certain high pressure compressor as the research object,the influence of the gas flow loss in the front transition section,transition section support plate and outlet transition section on compressor performance was simulated and studied by NUMECA software,and the structure modification and aerodynamic optimization of transition section were carried out based on DFFD parameter method and multiisland genetic algorithm.The results show that comparing with the compressor model without the transition section,the isentropic efficiency of the high pressure compressor is reduced by 1.57% with the prototype transition section,and that of optimized transition section is only reduced by 0.63% with the improvement of the transition section profile and the optimization design of the transition section support plate.After optimization,the gas flow blockage and loss in the transition section are reduced,and the whole efficiency of the high pressure compressor is increased by 0.94% compared with that before optimization.It is found that the main causes of blockage and efficiency reduction are the support plate section and outlet extension section through the analysis of flow field loss.

V231.3

国家科技重大专项（2017-Ⅱ-0006-0019）